WO2018101303A1 - ガスタービン用高温部品及びガスタービン - Google Patents

ガスタービン用高温部品及びガスタービン Download PDF

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Publication number
WO2018101303A1
WO2018101303A1 PCT/JP2017/042745 JP2017042745W WO2018101303A1 WO 2018101303 A1 WO2018101303 A1 WO 2018101303A1 JP 2017042745 W JP2017042745 W JP 2017042745W WO 2018101303 A1 WO2018101303 A1 WO 2018101303A1
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WIPO (PCT)
Prior art keywords
filter
cooling gas
porous
gas turbine
supply hole
Prior art date
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PCT/JP2017/042745
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English (en)
French (fr)
Japanese (ja)
Inventor
石黒　達男
Original Assignee
三菱重工業株式会社
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Publication date
Application filed by 三菱重工業株式会社 filed Critical 三菱重工業株式会社
Priority to CN201780067153.XA priority Critical patent/CN109891071B/zh
Priority to US16/345,879 priority patent/US11085326B2/en
Publication of WO2018101303A1 publication Critical patent/WO2018101303A1/ja

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    • B22F7/002—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of porous nature
    • B22F7/004—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of porous nature comprising at least one non-porous part
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    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/514—Porosity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • the present disclosure relates to a high-temperature component for a gas turbine and a gas turbine.
  • the gas turbine includes a compressor, a combustor, and a turbine.
  • the gas turbine sucks in air, compresses the air with the compressor, burns fuel with the combustor, generates high-pressure and high-temperature combustion gas, and rotates the turbine. And electricity and thrust can be generated by the output of the turbine of the gas turbine.
  • High-temperature components for gas turbines such as a combustor, a turbine stationary blade, a moving blade, and a split ring are cooled by cooling air because they are exposed to high-temperature combustion gas.
  • a part applicable to the gas turbine disclosed in Patent Document 1 includes a substrate on which cooling air supply holes are formed, and a porous layer formed on the substrate. The porous layer is disposed on the gas path side through which the combustion gas flows, and is cooled by the cooling air supplied through the cooling air supply holes flowing inside itself.
  • the gas turbine sucks various foreign matters such as sand particles in order to suck the atmosphere.
  • various foreign matters such as sand particles in order to suck the atmosphere.
  • the cooling air is not supplied to a part of the porous layer.
  • the temperature of the porous layer increases around the cooling air supply hole clogged with foreign matter, and the porous layer is locally overheated.
  • the porous layer constitutes a part of the main body, if a foreign substance adheres to the porous layer, cooling of a part of the surrounding porous layer is insufficient, and the porous layer is locally It will be overheated.
  • the object of at least one embodiment of the present invention is to provide a high-temperature component for gas turbine and a gas turbine in which clogging due to foreign matters in the porous portion is prevented and local overheating of the porous portion is prevented. Is to provide.
  • a high temperature component for a gas turbine includes: The main body, A porous part provided as at least a part of the main body part or on at least a part of the main body part, through which a cooling gas can pass; At least one filter disposed upstream of the porous portion in the flow direction of the cooling gas and capable of collecting foreign matter that cannot pass through the porous portion; Is provided.
  • the at least one filter is spaced apart from at least a part of the main body.
  • the cooling gas that has passed through the part of the filter that is not clogged joins in the space downstream of the filter, and the porous part Distributed to.
  • the porous part Distributed to.
  • the at least one filter includes a first filter and a second filter;
  • the first filter can collect foreign matters smaller than the second filter,
  • the first filter is disposed upstream of the second filter in the flow direction of the cooling gas.
  • the cooling gas flows into the second filter after the foreign matters are collected by the first filter capable of collecting smaller foreign matters. Even if the foreign matter is clogged in a part of the first filter, the cooling gas that has passed through the part of the first filter that is not clogged flows into the second filter of the first filter. Since the second filter has a coarser structure than the first filter, the cooling gas flowing into the second filter can flow in the second filter in a direction perpendicular to the thickness direction. For this reason, even if the cooling gas flows into the second filter with a non-uniform distribution, the non-uniform distribution is alleviated or eliminated when the cooling gas flows out of the second filter, and the second filter causes the cooling gas to flow into the porous portion. Will be distributed appropriately. By distributing the cooling gas using the second filter in this way, local overheating of the porous portion is prevented.
  • the at least one filter includes a first filter and a second filter;
  • the first filter can collect foreign matters smaller than the second filter,
  • the first filter is disposed downstream of the second filter in the flow direction of the cooling gas.
  • the foreign gas is collected by the first filter after the foreign gas is collected by the second filter. For this reason, the amount of foreign matter flowing into the first filter is reduced by the second filter, and the usable period of the first filter can be extended.
  • the cooling gas bypasses the clogged part of the second filter because the second filter has a coarser structure than the first filter. Can pass through. As a result, foreign substances are collected over a long period of time by the second filter and the first filter, and local overheating of the porous portion is prevented.
  • the porous part is provided on at least a part of the main body part, At least a part of the main body is provided with a cooling gas supply hole for supplying the cooling gas to the porous portion.
  • the at least one filter is disposed between the porous part and at least a part of the main body part.
  • the filter since the filter is disposed between the porous portion and the main body portion, the foreign matter that has passed through the cooling gas supply hole is collected by the filter, and local overheating of the porous portion is caused. Is prevented.
  • the cross-sectional area of the cooling gas supply hole gradually decreases as it approaches the outlet in the cooling gas flow direction
  • the at least one filter is disposed inside the cooling gas supply hole and on the inlet side of the cooling gas supply hole in the flow direction of the cooling gas.
  • the cross-sectional area of the cooling gas supply hole gradually decreases as it approaches the outlet in the flow direction of the cooling gas.
  • the inlet of the cooling gas supply hole is smaller than the outlet. wide.
  • the main body is provided with a cavity having a larger cross-sectional area than the cooling gas supply hole between the cooling gas supply hole and the porous part.
  • the porous part is wide via the cavity. Cooling gas can be supplied to the region. As a result, even if foreign matter that has passed through the cooling gas supply hole adheres to the porous portion, the cooling gas can be supplied to the porous portion through the periphery of the foreign matter, and local overheating of the porous portion is prevented. Is done.
  • the main body portion or the porous portion constitutes at least a part of any one of a moving blade, a stationary blade, a split ring, and a combustor.
  • the porous portion is prevented from being overheated locally in the moving blade, stationary blade, split ring or combustor as the high-temperature component for the gas turbine.
  • a gas turbine according to at least one embodiment of the present invention includes: The high temperature component for gas turbines as described in any one of said structure (1) thru
  • the porous portion is prevented from being overheated locally, so that the reliability of the gas turbine is improved.
  • a high-temperature component for a gas turbine in which clogging due to foreign matters in the porous portion is prevented and local overheating of the porous portion is prevented.
  • 1 is a diagram schematically showing a configuration of a gas turbine 1 to which a high temperature component for a gas turbine according to an embodiment of the present invention is applied.
  • 1 is a perspective view schematically showing one stationary blade applicable to a turbine as a high temperature component for a gas turbine according to an embodiment of the present invention.
  • 1 is a perspective view schematically showing one rotor blade applicable to a turbine as a high temperature component for a gas turbine according to an embodiment of the present invention. It is a perspective view showing roughly one division ring applicable to a turbine as a high temperature part for gas turbines concerning one embodiment of the present invention. It is a longitudinal cross-sectional view which shows schematically the split ring which concerns on one Embodiment of this invention.
  • an expression indicating that things such as “identical”, “equal”, and “homogeneous” are in an equal state not only represents an exactly equal state, but also has a tolerance or a difference that can provide the same function. It also represents the existing state.
  • expressions representing shapes such as quadrangular shapes and cylindrical shapes represent not only geometrically strict shapes such as quadrangular shapes and cylindrical shapes, but also irregularities and chamfers as long as the same effects can be obtained. A shape including a part or the like is also expressed.
  • the expressions “comprising”, “comprising”, “comprising”, “including”, or “having” one constituent element are not exclusive expressions for excluding the existence of the other constituent elements.
  • FIG. 1 is a diagram schematically showing a configuration of a gas turbine 1 to which a high-temperature component for gas turbine according to an embodiment of the present invention is applied.
  • the gas turbine 1 includes a compressor (compression unit) 3, a combustor (combustion unit) 5, and a turbine (turbine unit) 7.
  • the compressor 3 sucks and compresses the atmosphere to generate compressed air.
  • the combustor 5 is supplied with compressed air from the compressor 3 together with the fuel, and the combustor 5 generates high-temperature and high-pressure combustion gas by burning the fuel.
  • the turbine 7 rotates the rotating shaft 9 using combustion gas.
  • the rotating shaft 9 is connected to the compressor 3 and is connected to, for example, a generator (not shown).
  • the compressor 3 is driven by the torque output from the rotating shaft 9 and the generator generates power.
  • FIG. 2 is a perspective view schematically showing one stationary blade 11 applicable to the turbine 7 as the high-temperature component 10 for a gas turbine according to the embodiment of the present invention.
  • the plurality of stationary blades 11 are fixed to a housing (cabinet) 12 of the turbine 7 in a state where the stationary blades 11 are arranged in the circumferential direction of the rotating shaft 9.
  • the stationary blade 11 includes a blade portion 13 and platforms 15 and 17 disposed on both sides of the blade portion 13, and a combustion gas flow path (gas path) is defined between the platforms 15 and 17. Therefore, the surfaces of the platforms 15 and 17 facing the gas path and the surface of the blade 13 are exposed to the combustion gas.
  • FIG. 3 is a perspective view schematically showing one rotor blade 19 applicable to the turbine 7 as the high-temperature component 10 for a gas turbine according to one embodiment of the present invention.
  • the plurality of rotor blades 19 are fixed to the rotating shaft 9 in a state of being arranged in the circumferential direction of the rotating shaft 9.
  • the moving blade 19 includes a blade portion 21, a platform 23 disposed on one side of the blade portion 21, and a blade root portion 25 that protrudes from the platform 23 to the opposite side of the blade portion 21. Since the blade root portion 25 is embedded in the rotating shaft 9, the moving blade 19 is fixed to the rotating shaft 9.
  • the platform 23 is disposed so as to cover the rotating shaft 9, and the surface of the platform 23 on the wing portion 21 side defines a gas path. Therefore, the surface of the platform 23 facing the gas path and the surface of the blade portion 21 are exposed to the combustion gas.
  • the combustion gas collides with the blade portions 21 of the plurality of moving blades 19 and rotates the rotating shaft 9.
  • FIG. 4 is a perspective view schematically showing one split ring 27 applicable to the turbine 7 as the high-temperature component 10 for a gas turbine according to the embodiment of the present invention.
  • the plurality of split rings 27 are fixed to the housing 12 of the turbine 7 while being arranged in the circumferential direction of the rotating shaft 9.
  • the split ring 27 is disposed outside the rotor blade 19 in the radial direction of the rotary shaft 9, and the plurality of split rings 27 arranged in the circumferential direction surround the plurality of rotor blades 19 arranged in the circumferential direction.
  • the split ring 27 includes a wall portion 29 that forms an surrounding wall that surrounds the rotor blade 19, and engaging portions 31 and 33 for fixing the wall portion 29 to the housing 12.
  • the surface (concave curved surface) of the wall 29 on the moving blade 19 side defines a gas path, and the surface of the wall 29 facing the gas path is exposed to the combustion gas.
  • FIG. 5 is a longitudinal sectional view schematically showing a split ring 27 (27a) according to an embodiment of the present invention.
  • FIG. 6 is a longitudinal sectional view schematically showing a split ring 27 (27b) according to an embodiment of the present invention.
  • FIG. 7 is a longitudinal sectional view schematically showing a split ring 27 (27c) according to an embodiment of the present invention.
  • FIG. 8 is a longitudinal sectional view schematically showing a split ring 27 (27d) according to an embodiment of the present invention.
  • FIG. 9 is a longitudinal sectional view schematically showing a split ring 27 (27e) according to an embodiment of the present invention.
  • FIG. 10 is a longitudinal sectional view schematically showing a split ring 27 (27f) according to an embodiment of the present invention.
  • FIG. 11 is a longitudinal sectional view schematically showing a split ring 27 (27g) according to an embodiment of the present invention.
  • FIG. 12 is a longitudinal sectional view schematically showing a split ring 27 (27h) according to an embodiment of the present invention.
  • FIG. 13 is a longitudinal sectional view schematically showing a split ring 27 (27i) according to an embodiment of the present invention.
  • FIG. 14 is a longitudinal sectional view schematically showing a split ring 27 (27j) according to an embodiment of the present invention.
  • FIG. 15 is a longitudinal sectional view schematically showing a split ring 27 (27k) according to an embodiment of the present invention.
  • FIG. 16 is a longitudinal sectional view schematically showing a split ring 27 (271) according to an embodiment of the present invention.
  • FIG. 17 is a schematic cross-sectional view of the blade portion 21 of the rotor blade 19 according to an embodiment of the present invention.
  • FIG. 18 is a schematic cross-sectional view of the blade portion 13 of the stationary blade 11 according to the embodiment of the present invention.
  • the high-temperature component 10 for gas turbine includes a main body portion 40, a porous portion 42, and at least one filter 43.
  • the main body 40 constitutes a basic skeleton that forms the high-temperature component 10 for a gas turbine, and is constituted by, for example, a heat-resistant metal such as a Ni-based alloy, a ceramic matrix composite (CMC), or the like.
  • the CMC is formed, for example, a ceramic fiber such as SiC, Al 2 O 3, or the, by the ceramic matrix, such as, for example, SiC, Al 2 O 3, or the covering of ceramic fibers.
  • An intermediate layer such as BN is provided between the ceramic fiber and the ceramic matrix.
  • the porous part 42 is provided as at least a part of the main body part 40 or on at least a part of the main body part 40.
  • the porous part 42 constitutes a part of the wall of the high-temperature component 10 for gas turbine.
  • the porous part 42 constitutes a coating layer that covers the outer surface of the high-temperature component 10 for gas turbine.
  • the porous part 42 has minute pores (not shown), and the cooling gas can pass through the porous part 42 through the pores. That is, the porous part 42 has a fine cooling structure.
  • the cooling gas is, for example, air.
  • the porous part 42 is made of, for example, foam metal (porous metal) such as NiAl, ceramics such as porous yttrium-stabilized zirconia, or porous CMC.
  • foam metal porous metal
  • ceramics such as porous yttrium-stabilized zirconia, or porous CMC.
  • the pores of the porous portion 42 have an equivalent diameter De of several ⁇ m to several hundred ⁇ m.
  • the porous part 42 may be produced by a 3D printer, for example.
  • the filter 43 for example, foam metal such as NiAl, a laminate of wire mesh, porous CMC, or the like can be used.
  • the at least one filter 43 is disposed upstream of the porous portion 42 in the flow direction of the cooling gas, and can collect foreign substances that cannot pass through the porous portion 42. That is, the filter 43 can collect foreign matters that cause clogging in the porous portion 42.
  • the filter 43 has a filter function that can collect foreign substances that block pores having an equivalent diameter De of several ⁇ m to several hundred ⁇ m in the porous portion 42.
  • the cooling gas passage area in the filter 43 may be sufficiently larger than the cooling gas passage area in the porous portion 42.
  • the flow rate of the cooling gas passing through the porous portion 42 and the filter 43 is mainly determined by the passage area of the porous 42.
  • the passage area of the cooling gas in the filter 43 is four times the passage area of the cooling gas in the porous portion 42
  • the flow rate of the cooling gas in the filter 43 is the flow velocity of the cooling gas in the porous portion 42. 1/4 of this.
  • the pressure loss is determined by the square of the flow velocity
  • the pressure loss of the filter 43 is 1/16 that of the porous portion 42. In this case, the ratio of the pressure loss is 94% for the porous portion 42 and 6% for the filter 43.
  • the passage area of the filter 43 is reduced to three times that of the porous portion 42.
  • the flow rate of the cooling gas in the filter 43 is 1/3, and the pressure loss is 1/9.
  • the ratio of the pressure loss is 90% for the porous portion 42 and 10% for the filter 43.
  • the flow rate of the cooling gas in the porous portion 42 is proportional to the square root of the pressure loss, in this example, the flow rate when clogging occurs in 25% of the filter 43 is 2% before clogging occurs. % Reduction.
  • At least a part of the porous portion 42 is disposed on the gas path side in which the combustion gas flows in the high-temperature component 10 for gas turbine.
  • the gas turbine high-temperature component 10 has an internal space 44 separated from a gas path by a porous portion 42, and a cooling gas having a pressure higher than that of the combustion gas flowing through the gas path is supplied to the internal space 44.
  • the porous part 42 is subjected to, for example, convection cooling or microchannel cooling in which the cooling gas passes through the porous part 42 according to the pressure difference between the static pressure of the cooling gas in the internal space 44 and the static pressure of the combustion gas in the gas path. Cooled down.
  • the filter 43 collects foreign matter that cannot pass through the porous portion 42, so that the porous portion 42 is prevented from being clogged. As a result, local overheating of the porous portion 42 is prevented.
  • the at least one filter 43 is from at least a portion of the body portion 40 covered by the porous portion 42 as shown in FIGS. 5, 6, 9, 10, and 11.
  • the space (distribution space) 45 is spaced apart.
  • the cooling gas that has passed through the part of the filter 43 that is not clogged joins in the distribution space 45 downstream of the filter 43 and is porous. It is distributed to the mass part 42.
  • a groove or a slot (not shown) is provided in the main body 40, and the filter 43 can be held by inserting both ends of the plate-like filter 43 into the groove or the slot. If necessary, the filter 43 may be fixed by welding or an adhesive.
  • At least one filter 43 includes a first filter 43a and a second filter 43b.
  • the first filter 43a can collect foreign matters smaller than the second filter 43b.
  • the first filter 43a is disposed upstream of the second filter 43b in the cooling gas flow direction.
  • the cooling gas flows into the second filter 43b after the foreign matters are collected by the first filter 43a capable of collecting smaller foreign matters. Even if clogging occurs in a part of the first filter 43a due to foreign matter, the cooling gas that has passed through the portion of the first filter 43a that is not clogged flows into the second filter 43b downstream of the first filter 43a. Since the second filter 43b has a coarser structure than the first filter 43a, the cooling gas that has flowed into the second filter 43b passes through the layered second filter 43b in an in-plane direction perpendicular to the thickness direction. Can also flow.
  • At least one filter 43 includes a first filter 43a and a second filter 43b.
  • the first filter 43a can collect foreign matters smaller than the second filter 43b.
  • the first filter 43a is disposed downstream of the second filter 43b in the cooling gas flow direction.
  • the cooling gas collects a smaller foreign matter by the first filter 43a. For this reason, the amount of foreign matter flowing into the first filter 43a is reduced by the second filter 43b, and the usable period of the first filter 43a can be extended.
  • the second filter 43b has a coarser structure than the first filter 43a, so the cooling gas clogs the second filter 43b. You can pass around the part. As a result, foreign substances are collected over a long period of time by the second filter 43b and the first filter 43a, and local overheating of the porous portion 42 is prevented.
  • the at least one filter 43 further includes a third filter 43c, and the third filter 43c can collect a foreign object smaller than the first filter 43a. is there.
  • the third filter 43c is arranged downstream of the first filter 43a in the cooling gas flow direction. According to the said structure, after a foreign material is collected by the 2nd filter 43b and the 1st filter 43a, a smaller foreign material is collected by the 3rd filter 43c. For this reason, the amount of foreign matter flowing into the third filter 43c is reduced by the second filter 43b and the first filter 43a, and the usable period of the third filter 43c can be extended. That is, at least one filter 43 may be configured by one filter or a plurality of filters, and the number of filters is not particularly limited.
  • the equivalent diameter of the cooling gas flow path (internal flow path) in the first filter 43a is: It is smaller than the equivalent diameter of the internal flow path of the second filter 43b.
  • the equivalent diameter of the internal flow path of the third filter 43c is equal to the internal flow path of the first filter 43a so that the third filter 43c can collect foreign matter smaller than the first filter 43a. Is less than the equivalent diameter.
  • the equivalent diameter of the internal flow path of the filter 43 is not necessarily smaller than the equivalent diameter of the pores (internal flow path) of the porous portion 42.
  • the filter 43 can exhibit the filter function.
  • the equivalent diameter of the internal flow path of the filter 43 is larger than the equivalent diameter of the pores (internal flow path) of the porous portion 42, if the internal flow path of the filter 43 is long and winding, the foreign matter Are collected by repeated collisions in the internal flow path, and can exhibit a filter function. That is, the filter 43 should just be designed so that a foreign material can be collected as a whole.
  • the porous portion 42 is provided on at least a portion of the body portion 40 as shown in FIGS. .
  • the top of the main body 40 is on the outer surface of the main body 40, for example, on the gas path side.
  • a cooling gas supply hole 46 for supplying a cooling gas to the porous portion 42 is provided in at least a part of the main body portion 40 covered with the porous portion 42.
  • the filter 43 is disposed upstream of the cooling gas supply hole 46, foreign matters are collected by the filter 43, and clogging of the cooling gas supply hole 46 is prevented. As a result, local overheating of the porous portion 42 is prevented.
  • the filter 43 is disposed downstream of the cooling gas supply hole 46, the foreign matter that has passed through the cooling gas supply hole 46 is collected by the filter 43, and local overheating of the porous portion 42 is prevented. . Even if the filter 43 is disposed in the cooling gas supply hole 46, foreign matter is collected by the filter 43 and local overheating of the porous portion 42 is prevented.
  • At least one filter 43 is disposed between the porous portion 42 and at least a portion of the body portion 40. Yes. That is, the filter 43 is sandwiched between the porous portion 42 and the main body portion 40.
  • the filter 43 since the filter 43 is disposed between the porous portion 42 and the main body portion 40, foreign matter that has passed through the cooling gas supply hole 46 is collected by the filter 43, and the porous portion 42 is locally localized. Overheating is prevented.
  • the filter 43 may be fixed to the main body portion 40 by welding or an adhesive, and the porous portion 42 may be formed on the filter 43.
  • the main body 40 and the filter 43 may be joined by welding or an adhesive, and the filter 43 and the porous part 42 may be joined by an adhesive.
  • the cross-sectional area (flow channel area) of the cooling gas supply hole 46 gradually decreases as it approaches the outlet in the flow direction of the cooling gas.
  • the cooling gas supply hole 46 has a truncated cone shape.
  • the at least one filter 43 is disposed inside the cooling gas supply hole 46 and on the inlet side of the cooling gas supply hole 46 in the flow direction of the cooling gas.
  • the cross-sectional area of the cooling gas supply hole 46 gradually decreases as it approaches the outlet in the flow direction of the cooling gas.
  • the inlet of the cooling gas supply hole 46 is wider than the outlet. .
  • the cooling gas bypasses the clogged part of the filter 43 and passes through the cooling gas supply hole 46. be able to.
  • the filter 43 may be fixed to the main body 40 by welding or an adhesive.
  • the body 40 is provided with a cavity 48 having a larger cross-sectional area than the cooling gas supply hole 46 between the cooling gas supply hole 46 and the porous part 42.
  • the cavity 48 having a larger cross-sectional area than the cooling gas supply hole 46 is provided between the cooling gas supply hole 46 and the porous part 42, the porous part is interposed via the cavity 48.
  • the cooling gas can be supplied to a wide area of 42.
  • the cooling gas can be supplied to the porous portion 42 through the periphery of the foreign matter. Overheating is prevented.
  • the cavity 48 has, for example, a cylindrical shape or a prism shape that is coaxial with the cooling gas supply hole 46.
  • the cavity 48 may have a groove shape or a channel shape extending along the porous portion 42.
  • the cavity 48 is formed so that the cross-sectional area of the cavity 48 is as large as possible.
  • the cavities 48 are formed such that the walls separating adjacent cavities 48 are as thin as possible.
  • the porous portion 42 may constitute the entire main body portion 40 of the high-temperature component 10 for gas turbine.
  • a groove or slot (not shown) is provided in the porous portion 42 constituting the main body portion 40, and the end of the filter 43 is inserted into the groove or slot to hold the filter 43. Can do.
  • the filter 43 may be fixed by welding or an adhesive.
  • the porous portion 42 and the filter 43 may constitute a part of the main body portion 40.
  • the filter 43 may be fixed to the remaining portion of the main body portion 40 by welding, an adhesive, or the like, and the filter 43 and the porous portion 42 may be joined by welding, an adhesive, or the like. Or you may fix what formed the porous part 42 and the filter 43 integrally with respect to the remainder of the main-body part 40 with welding, an adhesive agent, etc. so that it may mention later.
  • a thermal barrier layer (TBC) 50 may be provided on the porous portion 42.
  • the heat shield layer 50 is made of, for example, ceramics such as yttrium stabilized zirconia, and has a porosity smaller than that of the porous portion 42.
  • a cooling gas discharge hole 52 through which the cooling gas flows out may be formed in the heat shield layer 50.
  • an adhesive layer (intermediate layer) 54 may be provided between the main body portion 40 and the porous portion 42.
  • the adhesive layer 54 joins the main body portion 40 and the porous portion 42, and is made of, for example, a material obtained by firing aluminum phosphate or an MCrAlY alloy.
  • M in the MCrAlY alloy represents one or more selected from the group consisting of Ni, Co, and Fe.
  • the MCrAlY alloy has a composition represented by Co-32Ni-21Cr-8Al-0.5Y.
  • the cross-sectional area (flow channel area) of the cooling gas supply hole 46 may gradually decrease as it approaches the outlet in the flow direction of the cooling gas.
  • the cooling gas supply hole 46 may have a truncated cone shape.
  • the porous portion 42 is provided at least on the outer surface side (gas path side) of the wall portion 29 of the split ring 27. In some embodiments, as shown in FIG. 17, the porous portion 42 is provided at least on the outer surface side (gas path side) of the blade portion 21 of the rotor blade 19. In some embodiments, as shown in FIG. 18, the porous portion 42 is provided at least on the outer surface side (gas path side) of the blade portion 13 of the stationary blade 11.
  • the main body portion 40 or the porous portion 42 constitutes at least a part of the split ring 27, the rotor blade 19 or the stationary blade 11 as the high-temperature component 10 for a gas turbine.
  • the high temperature component 10 for gas turbines is the combustor 5 as shown in FIG.
  • the main body 40 or the porous portion 42 constitutes at least a part of the combustor 5, for example, a combustion cylinder or a tail cylinder (transition piece).
  • the porous portion 42 is prevented from being overheated locally, like the moving blade 19, the stationary blade 11, or the split ring 27.
  • FIG. 19 is a flowchart schematically showing an example of a procedure of a method for manufacturing a porous portion applied to the high-temperature component 10 for a gas turbine according to an embodiment of the present invention.
  • the manufacturing method of the porous portion includes a slurry preparation step S1, an assembly preparation step S3, a slurry applying step S5, a drying step S7, and a heating step S9.
  • a slurry preparation step S1 as a raw material of the slurry, water as a solvent, such as distilled water or deionized water, ceramic powder, pore-generating powder, a dispersant as necessary, and a binder as necessary And are prepared. Then, the raw materials are stirred and mixed to prepare a slurry.
  • the ceramic powder is, for example, a powder containing one or more selected from the group consisting of SiC, Si 3 N 4 , ⁇ SiAlON, AlN, TiB 2 , BN, WC, and the like, or a raw material thereof.
  • the pore-generating powder is, for example, a powder containing one or more selected from the group consisting of organic materials, carbon, graphite and the like.
  • the organic material powder is, for example, an acrylic, styrene, or polyethylene polymer powder.
  • Dispersants include, for example, polycarboxylic acid ammonium salt, polycarboxylic acid sodium salt, neutralized polyphosphate amino alcohol, naphthalenesulfonic acid ammonium salt, polycarboxylic acid alkylamine salt, nonionic surfactant, and cationic system 1 type or more selected from the group which consists of surfactant etc. is included.
  • the binder includes, for example, one or more selected from the group consisting of polyvinyl alcohol resin, acrylic resin, and paraffin.
  • the assembly preparation step S3 an assembly of ceramic fibers is prepared.
  • the aggregate of ceramic fibers is a bundle of ceramic fibers or a woven fabric.
  • the ceramic fiber includes, for example, one or more selected from the group consisting of SiC, SiTiCO, SiZrCO, SiAlCO, Si 3 N 4 and the like, or a raw material thereof.
  • slurry is applied to the ceramic fiber aggregate.
  • the slurry is applied to the aggregate of ceramic fibers so that the slurry penetrates into the gaps between the ceramic fibers.
  • the aggregate of ceramic fibers is immersed in the slurry under a pressure lower than atmospheric pressure.
  • the slurry is applied to the aggregate of ceramic fibers by applying the slurry and then rolling the roller.
  • the drying step S7 the slurry applied to the aggregate of ceramic fibers is dried in an atmosphere of, for example, 120 ° C. to form a green body (intermediate body).
  • the green body is heated in a reducing atmosphere of, for example, 1200 ° C., the ceramic powder is sintered, and the pore generating powder is lost.
  • the pore-generating powder is mixed in the slurry in the slurry preparation step S1, and the pore-generating powder is eliminated in the heating step S9. Pore corresponding to the powder can be generated.
  • a porosity can be controlled by adjusting the quantity of the powder for pore production
  • FIG. 20 is a schematic perspective view for explaining an example of the assembly preparation step S3 and the slurry applying step S5.
  • a plurality of ceramic fiber fabrics 56 are provided.
  • the slurry is applied to each fabric 56, and the content and / or particle size of the pore-generating powder contained in the slurry to be applied is made different for each fabric 56. Therefore, in the slurry preparation step S1, a plurality of slurries having different contents and / or particle sizes of the pore-generating powder are prepared.
  • the porous part from which the porosity differs in the thickness direction can be manufactured by overlapping and drying and heating the textile fabric 56 which provided the slurry.
  • a layer having a high porosity in the porous portion can be used as a filter. That is, according to the above-described method, the porous portion and the filter layer can be manufactured integrally. Or according to the above-mentioned method, it is also possible to manufacture a main-body part and a filter layer integrally.
  • the split ring 27 has been mainly described as the high-temperature component 10 for a gas turbine.
  • the configuration described for the split ring 27 can be applied to the combustor 5, the stationary blade 11, and the moving blade 19.
  • the configuration described with reference to FIG. 5 can also be applied to the combustor 5, the rotor blade 19, and the split ring 27, and the configuration described with respect to the rotor blade 19 can be applied to the combustor 5, the stationary blade 11, and the split ring 27. .
  • the gas turbine high-temperature component 10 is a component that is at least partially heated to a temperature of, for example, 800 ° C. or more due to the influence of combustion gas.
  • the above-described combustor 5, stationary blade 11, moving blade 19, and The ring 27 is not limited.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Composite Materials (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
PCT/JP2017/042745 2016-11-30 2017-11-29 ガスタービン用高温部品及びガスタービン WO2018101303A1 (ja)

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US16/345,879 US11085326B2 (en) 2016-11-30 2017-11-29 Gas turbine hot part and gas turbine

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Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6622176B2 (ja) * 2016-11-30 2019-12-18 三菱重工業株式会社 ガスタービン用高温部品及びガスタービン
FR3098238B1 (fr) * 2019-07-04 2021-06-18 Safran Aircraft Engines dispositif de refroidissement amélioré d’anneau de turbine d’aéronef
US11326470B2 (en) * 2019-12-20 2022-05-10 General Electric Company Ceramic matrix composite component including counterflow channels and method of producing
WO2021127440A1 (en) * 2019-12-20 2021-06-24 Johnson Controls Technology Company Heat exchanger built with additive manufacturing
WO2023121680A1 (en) * 2021-12-20 2023-06-29 General Electric Company Wire screen particle filter for turbomachine airfoil

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001179028A (ja) * 1999-12-27 2001-07-03 Tokyo Electric Power Co Inc:The 洗浄再生形ガスタービン用エアフィルタ
JP2008032014A (ja) * 2006-07-31 2008-02-14 General Electric Co <Ge> シュラウドハンガ組立体及びガスタービンエンジン
US20110067378A1 (en) * 2009-09-21 2011-03-24 Rolls-Royce Plc Separator device
JP2016094916A (ja) * 2014-11-17 2016-05-26 三菱日立パワーシステムズ株式会社 ガスタービン構成部材及びガスタービン

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04113702U (ja) * 1991-03-26 1992-10-06 日産自動車株式会社 ターボ機械のコンプレツサハウジング
US6511762B1 (en) * 2000-11-06 2003-01-28 General Electric Company Multi-layer thermal barrier coating with transpiration cooling
US6617003B1 (en) * 2000-11-06 2003-09-09 General Electric Company Directly cooled thermal barrier coating system
US6443700B1 (en) * 2000-11-08 2002-09-03 General Electric Co. Transpiration-cooled structure and method for its preparation
US7144220B2 (en) * 2004-07-30 2006-12-05 United Technologies Corporation Investment casting
US9447503B2 (en) * 2007-05-30 2016-09-20 United Technologies Corporation Closed pore ceramic composite article
US8303247B2 (en) * 2007-09-06 2012-11-06 United Technologies Corporation Blade outer air seal
US9421733B2 (en) * 2010-12-30 2016-08-23 Rolls-Royce North American Technologies, Inc. Multi-layer ceramic composite porous structure
US8601691B2 (en) * 2011-04-27 2013-12-10 General Electric Company Component and methods of fabricating a coated component using multiple types of fillers
US9249672B2 (en) * 2011-09-23 2016-02-02 General Electric Company Components with cooling channels and methods of manufacture
DE102013109116A1 (de) 2012-08-27 2014-03-27 General Electric Company (N.D.Ges.D. Staates New York) Bauteil mit Kühlkanälen und Verfahren zur Herstellung
US9003657B2 (en) * 2012-12-18 2015-04-14 General Electric Company Components with porous metal cooling and methods of manufacture
JP2016035209A (ja) * 2014-08-01 2016-03-17 三菱日立パワーシステムズ株式会社 軸流圧縮機、及び軸流圧縮機を備えたガスタービン
JP6025941B1 (ja) * 2015-08-25 2016-11-16 三菱日立パワーシステムズ株式会社 タービン動翼、及び、ガスタービン
US10598026B2 (en) * 2016-05-12 2020-03-24 General Electric Company Engine component wall with a cooling circuit
US10612389B2 (en) * 2016-08-16 2020-04-07 General Electric Company Engine component with porous section
JP6856364B2 (ja) * 2016-11-30 2021-04-07 三菱重工業株式会社 ガスタービン用高温部品、ガスタービンの翼及びガスタービン
JP6622176B2 (ja) * 2016-11-30 2019-12-18 三菱重工業株式会社 ガスタービン用高温部品及びガスタービン

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001179028A (ja) * 1999-12-27 2001-07-03 Tokyo Electric Power Co Inc:The 洗浄再生形ガスタービン用エアフィルタ
JP2008032014A (ja) * 2006-07-31 2008-02-14 General Electric Co <Ge> シュラウドハンガ組立体及びガスタービンエンジン
US20110067378A1 (en) * 2009-09-21 2011-03-24 Rolls-Royce Plc Separator device
JP2016094916A (ja) * 2014-11-17 2016-05-26 三菱日立パワーシステムズ株式会社 ガスタービン構成部材及びガスタービン

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US20190249567A1 (en) 2019-08-15
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JP6622176B2 (ja) 2019-12-18
CN109891071B (zh) 2021-08-27
US11085326B2 (en) 2021-08-10

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